全文获取类型
收费全文 | 580篇 |
免费 | 131篇 |
国内免费 | 183篇 |
专业分类
航空 | 490篇 |
航天技术 | 158篇 |
综合类 | 64篇 |
航天 | 182篇 |
出版年
2024年 | 4篇 |
2023年 | 15篇 |
2022年 | 36篇 |
2021年 | 65篇 |
2020年 | 48篇 |
2019年 | 41篇 |
2018年 | 32篇 |
2017年 | 34篇 |
2016年 | 56篇 |
2015年 | 37篇 |
2014年 | 53篇 |
2013年 | 46篇 |
2012年 | 31篇 |
2011年 | 50篇 |
2010年 | 55篇 |
2009年 | 32篇 |
2008年 | 38篇 |
2007年 | 43篇 |
2006年 | 27篇 |
2005年 | 24篇 |
2004年 | 25篇 |
2003年 | 16篇 |
2002年 | 10篇 |
2001年 | 11篇 |
2000年 | 13篇 |
1999年 | 8篇 |
1998年 | 11篇 |
1997年 | 7篇 |
1996年 | 5篇 |
1995年 | 5篇 |
1994年 | 1篇 |
1993年 | 6篇 |
1992年 | 2篇 |
1991年 | 4篇 |
1989年 | 2篇 |
1988年 | 1篇 |
排序方式: 共有894条查询结果,搜索用时 15 毫秒
1.
针对飞机制造的装配序列规划问题,提出一种基于模因算法的飞机部件装配序列规划方法。在装配优先约束矩阵和非正交干涉矩阵的基础上构建装配规划模型,以飞机零部件间的装配方向和装配工具的差异性来构建适应度函数。在非干涉解空间中进行全局搜索,获得较优的装配规划方案,通过二叉树中序遍历法将较优的方案转化为可行解,再经过交叉操作和变异操作后,在可行解空间内进行局部搜索,最终获取较优的装配方案。以某型号的飞机舱门装配为例,通过与传统遗传算法对比,证实模因算法在飞机装配序列规划中的可行性和有效性。 相似文献
2.
Houman Hakima M. Reza Emami 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2021,67(7):2151-2171
This paper presents the mission design for a CubeSat-based active debris removal approach intended for transferring sizable debris objects from low-Earth orbit to a deorbit altitude of 100 km. The mission consists of a mothership spacecraft that carries and deploys several debris-removing nanosatellites, called Deorbiter CubeSats. Each Deorbiter is designed based on the utilization of an eight-unit CubeSat form factor and commercially-available components with significant flight heritage. The mothership spacecraft delivers Deorbiter CubeSats to the vicinity of a predetermined target debris, through performing a long-range rendezvous maneuver. Through a formation flying maneuver, the mothership then performs in-situ measurements of debris shape and orbital state. Upon release from the mothership, each Deorbiter CubeSat proceeds to performing a rendezvous and attachment maneuver with a debris object. Once attached to the debris, the CubeSat performs a detumbling maneuver, by which the residual angular momentum of the CubeSat-debris system is dumped using Deorbiter’s onboard reaction wheels. After stabilizing the attitude motion of the combined Deorbiter-debris system, the CubeSat proceeds to performing a deorbiting maneuver, i.e., reducing system’s altitude so much so that the bodies disintegrate and burn up due to atmospheric drag, typically at around 100 km above the Earth surface. The attitude and orbital maneuvers that are planned for the mission are described, both for the mothership and Deorbiter CubeSat. The performance of each spacecraft during their operations is investigated, using the actual performance specifications of the onboard components. The viability of the proposed debris removal approach is discussed in light of the results. 相似文献
3.
Mingying Huo Giovanni Mengali Alessandro A. Quarta 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2018,61(10):2617-2627
Propellantless continuous-thrust propulsion systems, such as electric solar wind sails, may be successfully used for new space missions, especially those requiring high-energy orbit transfers. When the mass-to-thrust ratio is sufficiently large, the spacecraft trajectory is characterized by long flight times with a number of revolutions around the Sun. The corresponding mission analysis, especially when addressed within an optimal context, requires a significant amount of simulation effort. Analytical trajectories are therefore useful aids in a preliminary phase of mission design, even though exact solution are very difficult to obtain. The aim of this paper is to present an accurate, analytical, approximation of the spacecraft trajectory generated by an electric solar wind sail with a constant pitch angle, using the latest mathematical model of the thrust vector. Assuming a heliocentric circular parking orbit and a two-dimensional scenario, the simulation results show that the proposed equations are able to accurately describe the actual spacecraft trajectory for a long time interval when the propulsive acceleration magnitude is sufficiently small. 相似文献
4.
5.
通过分析对比,详细介绍了南飞公司应用工业工程重新规划和改进钣金车间生产现场的作法,以及所取得的技术经济效果。 相似文献
6.
7.
为减小运动部件加减速过程中对整个平台的冲击,在进行运动轨迹规划时,采用了S形曲线对定位系统的运动轨迹进行了平滑处理,有效地降低了运动部件对系统的冲击,有利于系统的减振。 相似文献
8.
9.
10.
用户在制定卫星观测计划时,需要知道卫星的星下点位置以及遥感器对地扫描区域的信息。通常这些信息是以数值描述的形式发给用户的,不够直观。本文介绍了一种基于WebGIS的卫星观测计划编制系统,介绍了WebGIS在计划编制系统中的应用,并从系统设计、功能、利用WebGIS进行计划策略判断方案等方面进行了深入讨论。 相似文献